叶顶喷气对跨音速轴流压气机稳定裕度影响的数值研究

Numerical Study of the Effect of Tip Injection on the Stability Margin of Transonic Axial Compressor

为了研究叶顶喷气机匣处理方式对轴流压气机稳定裕度的影响,针对Rotor37开展了叶顶喷气的定常数值研究。相关文献指出,喷嘴出口气流角、喷嘴轴向位置、喷嘴覆盖比率及喷嘴进口总压4个参数对稳定裕度的影响最为显著。因此,本文着重对这四个参数构建响应面,同时结合主流的单通道计算模型,详细分析了它们之间的交互关系及相应的参数变化对压气机稳定性的影响,并拟合出回归方程。结果显示,在最佳参数设置下,单通道计算模型中压气机的稳定裕度最大可以增加8%左右。在此基础上,又对四通道压气机计算模型进行了气动计算与分析,发现叶顶喷气射流会按照与压气机旋转相反的方向作用于相邻的叶片流道,抑制该流道泄漏涡的产生,进而改善该流道内的流动。研究表明,采用叶顶喷气方法可以降低叶片前缘载荷,改变压气机的失速类型,从而增加压气机的稳定裕度。

In order to study the effect of tip jet casing treatment on the stability margin of axial flow compressor,a steady numerical study of tip jet was carried out for Rotor37.Relevant literature points out that the four parameters of nozzle outlet air flow angle,nozzle axial position,nozzle coverage ratio and nozzle inlet total pressure have the most significant impact on the stability margin.Therefore,the response surface is constructed for these four parameters in this paper.At the same time,combined with the mainstream single-channel calculation model,the interaction between them and the impact of corresponding parameter changes on the compressor stability are analyzed in detail,and the regression equation is fitted.The results show that under the optimal parameter setting,the maximum stability margin of the single-channel calculation model can be increased by about 8%.On this basis,the aerodynamic calculation and analysis of the four-channel compressor calculation model were carried out,and it was found that the tip jet would act on the adjacent blade passage in the opposite direction of the compressor rotation,inhibit the generation of leakage vortex in the passage,and then improve the flow in the passage.The research shows that the tip injection method can reduce the blade leading edge load,change the stall type of the compressor,and increase the stability margin of the compressor.